涡轮叶栅冷气掺混数值模拟方法  

Numerical Method for Coolant Mixing in Turbine Cascade Flow Field

作　　者：王松涛[1] 颜培刚[1] 孙玺淼[1] 韩万金[1] 王仲奇[1] 

机构地区：[1]哈尔滨工业大学能源科学与工程学院,黑龙江哈尔滨150001

出　　处：《航空动力学报》2003年第4期558-562,共5页Journal of Aerospace Power

基　　金：国家科技部973资助项目(G1999022307);哈尔滨工业大学校基金资助项目(HIT200076)

摘　　要：采用具有三阶精度TVD性质的有限差分格式、自由型曲面网格生成技术以及分区网格算法,对某型涡轮叶栅进行了任意数目冷气孔的薄膜冷却全三维N-S方程数值求解,较为详细的阐述了冷气掺混流场中卵型涡的发展规律。结果表明,本文所开发的求解系统能够较好的实现任意分区的流场求解,对涡轮叶栅中冷气喷射流场的描述是合理的。Threedimensional NS equation is discretized by a finite difference scheme with threeorder TVD property.Arbitrarilycurved surface generation technique and multiblock method are employed to simulate the filmcooling flow field in a turbine cascade with arbitrary numbers of coolant holes.The development of counterrotating vortices in coolantmixing flow field is expounded,including its origination,disappearing and the distribution of temperature near coolant trajectory.The result shows that the solver with domains arbitrarily decomposed developed in this paper can simulate the flow field well,and the description of coolant jet flow field in the turbine cascade is reasonable.

关 键 词：薄膜冷却技术 数值模拟 燃气涡轮 冷气掺混 涡轮叶栅 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]